3. Abstract
Introduction
Design stages
_ Controller Design
_ Elevator-Theta control
Aileron phi controller
Multivariable control system design
HIL Test Platform
S.W.O.T Analysis
Conclusion And Future Work
References
4. This paper enlightens
Hardware-In-the-Loop (HIL) test platform is used
to design a flight stabilization system for (UAV).
Controllers are first designed and tested separately
for lateral and longitudinal axes using numerical
simulations.
It is observed that the resulting controller
successfully stabilizes the aircraft to achieve
straight and level flight.
5. Aeronautics has recently gained great importance
in both military and civil applications .
These systems perform autonomous flights &
mission can be done without human input .
To remain air plane in steady uniform state, the
resultant on plane and resultant acting on earth
must be zero or uniform.
A suitable flight condition is designed by
MATLAB/Simulink environment simulation to
design a controller for UAVs
6. The stability and control of airplanes requires a study of
the dynamics of flight.
Elevators and ailerons are flight control surfaces.
Elevators are surfaces on the tail plane .
Ailerons are surfaces on the outer, trailing edge of each
wing. They angle in opposite directions to waggle the
wings up and down or roll the aircraft about its nose -
tail axis.
This is the approach in what is commonly known as
static stability and control analysis
7. Aircraft have a number of different control surfaces those indicated in red
form the primary flight control, i.e. pitch, roll and yaw control, basically
obtained by deflection of elevators, ailerons and rudder .
Those indicated in blue form the secondary flight control; high-lift and lift-
dump devices, airbrakes, tail trimming.
Elevator angle is given as an input to the Simulink model and theta angle is
as an output. Firstly, Airlib library in MATLAB is used for the aircraft dynamic
model. Cessna 172 flight model’s aerodynamic derivatives are followed up.
8. Closed loop step response provided by PID controller and the input which is
applied.
PID control structure is built for supported flight mode applied to the
Simulink model’s input which is the change of the elevator angle.
9. Aileron is the control surface which operates the rolling of the UAV. This surface is
the input of the MATLAB model. The output is the phi angle which is the rolling
angle.
After linearization based on the operation point and obtained system’s minimal
implementation and PID controller’s transfer function is calculated by MATLAB
sisotool.
PID control structure is built for supported flight mode applied to the Simulink
model’s input which is the change of the aileron angle.
Designed controller’s impact of the other angles can be seen in the Fig. 7 and Fig.
8. When the UAV roll over to its side the theta angle should change a bit because
of the flight dynamics cross impacts. Besides UAV will trun in time which means
psi angle will change
10. Classical control tools have been popular for analysis and design of
Single-Input, Single-Output (SISO) systems [7]. These methods may be
viewed as specialized versions of more general tools that are applicable
to Multi-Input, Multi-Output (MIMO) systems
“state-space” control methods have been promoted as the predominant
tools for multivariable system analysis, the classical control extensions
offer several advantages, including requiring only an input-output map
and providig direct insight into stability, performance, and robustness of
MIMO systems
It is needed to be checked as if the elevator -theta and aileron -phi
single input single output system controllers are working together. For
this reason, both SISO system controllers are implemented at the same
time.
11. For the design, implementation and testing of control systems
Hardware-In-the-Loop (HIL) simulation is increasingly being
required, where some of the control-loop components are real
hardware, and some are simulated.
State space matrixes are gathered with calculations which explained
before aren’t always suitable for controlling UAVs.
HIL simulation is chosen because actual autopilot and its Inertial
Measurement Unit (IMU) can be integrated with simulation.
This HIL simulation technique needs simulation software and a
platform that use to integrate real values to simulation
Ardupilot mega 2.0 is used as autopilot. Because Ardupilot has its
own microcontroller, 6 DOF IMU and barometer, it is chosen. Also it
is easy to program Ardupilot.
12. HIL simulation performs as follows. Plane fly in the
Xplane generate roll and pitch angle values.
Platform’s microcontroller reads these values as
reference values for pitch axis PID
13. Strong point:
It is observed that the resulting controller successfully stabilize the aircraft to achieve
straight level flight & also used in military & civil application.
These system perform autonomous flight.
Weak points:
it is an controller based system which is sensitive and be careful during using because it
is much dangerous for us.
Opportunities:
Increased aircraft demand.
Rising global defense.
Threat:
In critical condition like rain, technical issues auto pilot airplane is not good & make
danger for us.
14. In this paper we outlined the design of elevator and aileron
stabilizer for UAVs and using data obtained from Xplane
simulation.
These models are used to construct PID controllers for these
surfaces and hardware in the loop simulations using a custom
3 degree of freedom moving platform confirm that the
designed controllers successfully.
In future work surface loss scenarios are considered and to
eliminate the impact of these losses controllers will be
developed based on this study.
15. Şeyma Akyürek, Gizem Sezin Özden, Emre Atlas,
and Coşku Kasnakoğlu , “Electrical & Electronics
Engineering, TOBB University of Economics &
Technology, Ankara, “ , ”Design of a Flight
Stabilizer System and Automatic Control Using HIL
Test Platform” ,IJMERR , 1, January 2016
